JP6124561B2 - Composite repair methods - Google Patents

Description

  The present invention relates to a method for repairing a composite material. It also relates to repaired composite materials.

A composite material formed of carbon fiber reinforced plastics (CFRP) or the like is used for an outer plate (skin) that forms the outer surface of an aircraft wing. The composite material is configured by laminating a plurality of CFRP sheets.
The outer plate is spaced from the front and back of the wing and is assembled in a box shape with spars that form the leading and trailing edges of the wing. The inside of the box is provided with ribs for supporting the outer plates on the front and back sides, and serves as a housing space for various devices and fuel.
By the way, if the outer plate is damaged by impact, repair is required. In the repair, the damaged portion where the layers are separated by impact is removed, and the recess formed by the removal is filled with the composite material. I would like to perform this repair without disassembling the box-like structure.

If the damaged part does not reach the back side of the outer plate, it can be repaired by accessing from the outer plate surface side (one side) without disassembling the structure.
For example, a repair material, which is a composite material similar to the outer plate body and is semi-cured, is disposed on the film-like adhesive in the recess formed by removing the damaged portion from the surface side. Then, after the repair material and the composite material are brought into close contact with each other through the adhesive film by evacuation from the surface side, the repair material can be bonded to the composite material by heating and curing the repair material. The concave portion of the composite material preferably has a uniform shape in all directions in order to avoid stress concentration, and is formed in a mortar shape having a circular shape in plan view by scarf processing.

On the other hand, when the damaged part extends to the back side of the outer plate, the recess formed by removing the damaged part penetrates the composite material in the thickness direction and opens on both the front side and the back side. Since the through-hole to be formed is formed, it is necessary to close the back surface side when evacuating. For this purpose, an operator is placed on the back side, but the structure must be disassembled if there is no space for the operator in the box.
Non-Patent Document 1 describes that in order to close the back surface side of the through hole, the through hole and the patch that closes the through hole have an oval shape. Unlike the case where the through-hole and the patch are circular with substantially the same diameter, if the patch is erected so that the major axis of the through-hole is aligned with the minor axis of the patch, the patch can be moved to the back side of the composite material. And the back surface side of a through-hole is sealed with the patch rotated on the back surface side. That is, repair without evacuation can be performed by evacuation from the surface side of the composite material.

Aircraft Icing Handbook, Report # DOT / FAA / AR-08 / 54 Composite Maintenance and Repair Issues

According to the method of Non-Patent Document 1, it is necessary to make the through-hole formed in the composite material elliptical by removing the damaged portion. However, in this method, it takes time and labor to form the elliptical through hole. Moreover, since it is necessary to examine the strength of the repaired part in each product in order to determine the direction of the major axis of the ellipse, it takes time to start repairing.
From the above, it is difficult to adopt the technique of making an ellipse.

  The present invention has been made based on the above problems, and an object thereof is to provide a practical repair method by access from one side when the entire thickness direction of the composite material is damaged.

The method for repairing a composite material according to the present invention removes a frustum-shaped range that expands from the back surface side to the front surface side in a plate-shaped composite material formed of fibers and resin, and the composite material is removed. Glue the repair material to replace the part.
The repair method of the present invention includes a removal step, a back surface side sealing step, a repair material placement step of placing the repair material with an adhesive interposed in the composite material from which the frustum-shaped range is removed, and the front surface side. And evacuating step for sealing and evacuating.
According to the present invention, in the removing step, a range including the range from the top surface to the projection area of the top surface at the bottom surface of the frustum is left on the surface side, leaving a support wall protruding radially inward from the peripheral portion of the top surface of the frustum. In the sealing step, the back surface side is sealed by installing on the support wall a sealing plate inserted from the front surface side into the through-hole formed by the removal. To do.

According to the present invention, repair can be performed only from one side (front side) of the composite material. In the present invention, one side of the composite material that the repair operator faces is called the front side, and the opposite side is called the back side.
In the present invention, leaving the support wall located on the back side of the composite material, removing the damaged portion from the composite material, and installing a sealing plate on the support wall, the back side of the composite material penetrated by the removal Is sealed. For this reason, in order to seal the back surface side, it is not necessary to form an elliptical through-hole as in the conventional method, and to apply the patch from the through-hole to the back surface side of the composite material. For this reason, in this invention, since the shape of a through-hole can be made into the perfect circle which can suffice with general-purpose processing, the strength examination and complicated ellipse processing for setting the direction of an ellipse major axis become unnecessary. As a result, the repair time can be shortened and the cost required for repair can be suppressed.
As described above, when repairing a composite material that is damaged in the entire thickness direction, it can be repaired without disassembling the structure even if there is no space for the operator on the back side. .

In the composite material repair method of the present invention, in the removing step, the range from the top surface to the projection region is removed from the frustum-shaped range of the composite material, and after the sealing plate is installed on the support wall, the frustum It is preferable to remove the remainder of the shape range.
If it carries out like this, since the surface of a sealing board will become a guide surface of a tool, processing will become easy.

In the method for repairing a composite material of the present invention, a frustum-shaped support wall slope that increases in diameter from the back surface side to the front surface side is formed on the support wall, and the sealing plate is sealed against the support wall slope. A stop plate slope can also be formed.
According to this, the stress which arises in a composite material can be disperse | distributed with the slope of a sealing plate and a support wall. As a result, the sealing plate cannot be made very thin to ensure stress, and therefore even if the height of the bonding surface of the composite material and repair material to be scarf-joined cannot be secured sufficiently, stress concentration is avoided. it can.

In the composite material repairing method of the present invention, in the removing step, the frustum-shaped range of the composite material is removed, and the peripheral edge portion on the back surface side of the frustum-shaped through hole formed by the removal is used as a support wall. You can also.
If it does in this way, since a support wall and the adhesion surface of a composite material and a repair material can be formed at once by scarf processing, repair can be facilitated.

The present invention is also established as a repaired composite material.
The composite material of the present invention is a composite material repaired by being bonded to a repair material disposed in a through-hole formed in the thickness direction while being formed into a plate shape with fibers and a resin.
In the present invention, a frustum-shaped repair material whose diameter increases from the back surface side to the front surface side and a sealing plate whose surface faces the top surface of the repair material are disposed in the through hole, and sealed. The plate is characterized in that the back surface side of the through hole is sealed by being installed on a support wall formed integrally with the composite material on the back surface side.

  In the composite material of the present invention, the support wall is formed with a frustum-shaped support wall slope that increases in diameter from the back side to the front side, and the sealing plate has a sealing plate slope that faces the support wall slope. Is preferably formed.

It is preferable that the composite material of the present invention described above constitutes an outer panel of an aircraft.
An aircraft wing or fuselage includes a skin and a support member that supports the skin from the inside. Since there are support members, fuel tanks and various devices inside the wings and fuselage, it is difficult to repair the outer plate from the inside. Therefore, when the composite material of the present invention is used for an outer panel of an aircraft, the effect of the present invention in which repair can be realized by access from only one side stands out.

According to the repair method of the present invention, it is possible to provide a realistic repair method by accessing from one side when the entire thickness direction of the composite material is damaged.
The composite material of the present invention can also enjoy the same effect.

It is a flowchart which shows each step of the repair method of the composite material which concerns on 1st Embodiment. It is sectional drawing which shows the repair step of a composite material. It is sectional drawing which shows the repair step of a composite material. It is sectional drawing which shows the repaired composite material. It is sectional drawing which shows the repair method of the composite material which concerns on 2nd Embodiment, and the repaired composite material.

Hereinafter, the present invention will be described in detail based on embodiments shown in the accompanying drawings.
[First Embodiment]
A method of repairing a damaged composite material by access from one side (surface side) and the repaired composite material will be described.
The composite material 10 to be repaired is formed by laminating a plurality of CFRP sheets. Instead of CFRP, fiber reinforced resin such as glass fiber reinforced plastics (GFRP) can be used.
This composite material 10 forms an outer plate that forms the outer surface of the main wing or tail wing of an aircraft, and is assembled in a box shape together with spars and ribs to constitute a structure.
The repair is done without disassembling the structure.
First, as shown in FIG. 1, the damaged portion 11 of the composite material 10 is inspected by ultrasonic flaw detection (step S1). Ultrasonic flaw detection can be performed from the surface 10A side (outside the box) of the composite material 10 by a known apparatus and method.

  The damaged portion 11 has a plurality of portions where the layers are separated as schematically shown in FIG. The range in which the peeling exists is specified by the above inspection. The range is removed in a truncated cone shape (indicated by a one-dot chain line) having the bottom surface on the surface 10A side. The entire range where the delamination exists is included in the range of the truncated cone 30 and the repair design is performed according to the inspection result so as to withstand the stress that can act on the composite material 10. Specifically, the diameter D 1 of the bottom surface 31 of the truncated cone, the diameter D 2 of the top surface 32 facing the bottom surface 31, and the inclination angle θ formed by the inclined surface 33 connecting the bottom surface 31 and the top surface 32 with respect to the bottom surface 31. To design. The bottom surface diameter D1, the top surface diameter D2, and the inclination angle θ are designed in consideration of the thickness T (FIG. 4) of the support wall 14 and the sealing plate 15 described later.

Here, when the damaged portion 11 extends to the back surface 10B side of the composite material 10, in order to remove it, a mortar-shaped recess penetrating from the front surface 10A side of the composite material 10 to the back surface 10B is formed. .
In the present embodiment, in order to realize repair by access from one side, first, the composite material 10 is penetrated in the thickness direction, and the through hole 12 having an opening diameter D corresponding to the diameter D2 of the truncated cone top surface 32 is formed. 10 from the surface 10A side, a part of the damaged portion 11 is removed. At this time, on the back surface 10B side of the through hole 12, the support wall 14 protruding inward in the radial direction is left without being removed, so that the support wall 14 is formed integrally with the composite material 10 (step S2 and FIG. 2B). )). Thereby, the range from the top surface 32 when the truncated cone 30 is assumed to the composite material 10 to the projection region of the top surface 32 on the bottom surface 31 is removed.

The support wall 14 is formed in an annular shape having an inner shape and an outer shape over the entire circumference of the through hole 12. The back surface of the support wall 14 is continuous with the back surface 10 </ b> B of the composite material 10. The thickness of the support wall 14 and the sealing plate 15 shown below is preferably as thin as possible with respect to the thickness of the composite material 10 in order to ensure a concave slope 18 described later as wide as possible. On the other hand, the support wall 14 and the sealing plate 15 are secured to such a thickness that the strength to withstand vacuuming can be obtained.
The width of the support wall 14 in the radial direction is arbitrary as long as the damaged portion 11 in the vicinity of the back surface 10B can be removed and the sealing plate 15 can be pressed during evacuation.

  The processing method of the through-hole 12 and the support wall 14 is arbitrary. For example, after forming a hole having an opening diameter facing the inner diameter of the support wall 14 through the entire thickness of the composite material 10, the hole is expanded to the opening diameter D except for a portion where the support wall 14 is formed. Thus, the through hole 12 and the support wall 14 can be formed. Alternatively, once drilling is performed using a tool having a blade that drills only a range corresponding to the inner diameter of the support wall 14 and a blade that is positioned behind the blade in the drilling direction and drills with an opening diameter D. The through hole 12 and the support wall 14 can also be formed.

Next, a perfect circular sealing plate 15 having a diameter equivalent to the opening diameter D of the through hole 12 is inserted into the through hole 12 from the front surface 10A side, and the back of the through hole 12 (on the back surface 10B side). Installation (step S3 and FIG. 2 (c)). The sealing plate 15 is supported on the surface of the support wall 14.
This sealing plate 15 is used for sealing the back surface 10B side in vacuuming described later. The sealing plate 15 is composed of a CFRP sheet similar to that constituting the composite material 10. Depending on the thickness of the sealing plate 15, one or more CFRP sheets are used for the sealing plate 15.
The sealing plate 15 is adhered to the surface of the support wall 14 by an adhesive (not shown) applied to the peripheral portion on the back surface side of the sealing plate 15 before being inserted into the through hole 12. Thereby, the gap between the sealing plate 15 and the support wall 14 is sealed.

Subsequently, by scarf processing, the remaining part where the damaged part 11 remains in the range of the truncated cone 30 is scraped off to remove the entire damaged part 11 (step S4 and FIG. 3A). This scarf processing is performed from the vicinity of the periphery of the surface 15A of the sealing plate 15 in order to enlarge the area where the composite material 10 and the repair material 20 described later are bonded and to relieve stress concentration at the bonded portion. A concave slope 18 that extends toward the surface 10A side of the material 10 is formed. The scarf processing is performed from the surface 10A side of the composite material 10 to the position of the surface 15A of the sealing plate 15. The surface 15A of the sealing plate 15 serves as a guide surface for the tool.
The concave slope 18 is inclined at the aforementioned inclination angle θ with respect to the back surface 10B. As described above, the inclination angle θ is determined by the range of the damaged portion 11 and the stress that can act on the composite material 10. For example, the radius of the concave slope 18 is 10 to 30 with respect to the thickness 1 of the composite material 10. Is set.
The concave slope 18 forms a mortar-shaped through recess 13 whose volume is larger than that of the through hole 12. The concave slope 18 is formed in a range obtained by subtracting the thickness T (FIG. 4) of the support wall 14 and the sealing plate 15 from the entire thickness of the composite material 10.

And the repair material 20 which is the same prepreg as used at the time of manufacture of the composite material 10 is arrange | positioned in the penetration recessed part 13 (step S5 and FIG.3 (b)). A prepreg is an intermediate material made by impregnating a sheet-like carbon fiber with a semi-cured thermosetting resin such as epoxy resin or polyimide, and is easy to process because the resin is not cured. In addition, the property is stabilized by controlling the blending amount of the resin to be constant, and the quality is high in terms of homogeneity. A prepreg produced by either a dry method or a wet method can also be used. For the sealing plate 15, a cured prepreg is used.
The repair material 20 has a truncated cone shape corresponding to the shape of the through recess 13, and its bottom surface diameter, top surface diameter, and inclination angle are the same as the above-described bottom surface diameter D1, top surface diameter D2, and inclination angle θ. Has been. The surface 10A of the composite material 10 and the surface 20A of the repair material 20 are substantially flush with each other.
A prepreg that exhibits the same strength as the composite material 10 after curing is selected as the repair material 20. This is to avoid stress concentration at the boundary between the repair material 20 and the composite material 10 (base material).
Between the concave slope 18 of the composite material 10 and the slope 20C of the repair material 20 facing it, and between the surface 15A of the sealing plate 15 and the back surface 20B of the repair material 20 facing it, thermosetting resin is used. A formed film or the like (not shown) is disposed as an adhesive AD (FIG. 4) for bonding the composite material 10 and the repair material 20. As long as the composite material 10 and the repair material 20 are used for bonding, the form and properties of the adhesive AD are not limited.

  Next, vacuuming is performed using a vacuum pump (not shown) (step S6 and FIG. 3C). At this time, the surface 20 </ b> A of the repair material 20 and its periphery are covered with a heat-resistant back film 21. The space between the back film 21 and the surface 10 </ b> A of the composite material 10 is sealed by the sealant tape 22 disposed around the surface 20 </ b> A of the repair material 20. The sealant tape 22 is formed in a string shape from a sealant material having heat resistance and adhesion, and is arranged in an annular shape so as to surround the repair material 20 on the surface 10A.

When the vacuum pump is operated, the gap between the composite material 10 and the repair material 20 sandwiched between the back film 21 and the sealing plate 15 is decompressed via the vacuum valve 23 provided in the back film 21. At this time, since the sealing plate 15 is pressed by the support wall 14 due to the pressure difference from the atmospheric pressure, the sealing by the back film 21 and the sealing plate 15 can be maintained. Moreover, since the sealing plate 15 is formed of the same material as the composite material 10 and has high strength and high quality from the viewpoint of strength uniformity, it is uniform in the gap without being deformed during suction. The pressure can be reduced to a desired degree of vacuum while applying an appropriate pressure. Thereby, since the mutually opposing surface of the composite material 10 and the repair material 20 can be made to closely_contact | adhere on both sides of adhesive agent AD, high adhesive quality is obtained.
The vacuum valve 23 is positioned between the outer peripheral edge of the surface 20A of the repair material 20 and the sealant tape 22 in order to prevent the surface 20A of the uncured repair material 20 from being depressed by the vacuum valve 23. It is provided on the composite material 10 to be made.

Thereafter, the repair material 20 and the adhesive AD are heated and cured by appropriate heating means (step S7 and FIG. 3D). Even in this step, it is preferable to continue evacuation.
In the present embodiment, a heater mat 24 incorporating a heater is disposed on the back film 21 and heated. Other types of heaters and dryers can be used as the heating means. The heating means can be arbitrarily configured regardless of the heat propagation method. The structure to be repaired can also be heated in an oven.
When the repair material 20 and the adhesive AD are cured, the repair material 20 is bonded to the composite material 10. Since the composite material 10 and the repair material 20 are in close contact with each other by evacuation, the two are firmly integrated with uniform adhesive strength.
The repair of the composite material 10 is completed by the above procedure. Each of the repair steps described above is performed from the surface 10A side of the composite material 10.
FIG. 4 shows the repaired composite material 10.

In the repair method of this embodiment, the support wall 14 is formed on the back surface 10B side of the through recess 13 formed by removing the damaged portion 11, and the back surface 10B of the through recess 13 is formed by the sealing plate 15 installed there. The side is sealed. For this reason, in order to seal the back surface 10B side of the through recess 13, it is not necessary to form an elliptical through recess as in the conventional method and attach the patch inserted into the through recess to the back surface 10B. For this reason, the planar shape of the penetration recessed part 13 is made into the perfect circle which needs a general-purpose process. This eliminates the need for strength examination and complicated ellipse processing for setting the orientation of the ellipse major axis, thereby reducing the repair time and reducing the cost required for repair.
In this embodiment, since the sealing plate 15 is supported on the front surface side of the support wall 14, the patch is suspended in order to prevent dropping when the patch is moved to the back surface side as in the conventional method. Is also unnecessary. In addition, the sealing plate 15 can be positioned by the surface of the support wall 14 and the inner wall of the through hole 12. This facilitates repair work.

According to this embodiment described above, even if there is no space for the operator to enter on the back surface 10B side (inside the structure), it can be repaired without any trouble. Therefore, repair by access from one side (surface side) can be realized over the entire surface of the composite material 10 without disassembling the structure. Since disassembly is unnecessary, repairs can be carried out at a reduced cost.
The composite material 10 repaired by the repair method of the present embodiment can also enjoy the effects described above.

  In addition, instead of designing the bottom surface diameter D1, the top surface diameter D2, and the inclination angle θ each time according to the inspection result of the damaged portion 11, the dimensional shape and stress of the damaged portion 11 are standardized into a plurality of shapes. It is also possible to prepare a plurality of patterns of a set of bottom surface diameter D1, top surface diameter D2, and inclination angle θ suitable for the above. As a result, it is sufficient to apply the inspection result of the damaged portion 11 to any one of the patterns, so that the design for repair is facilitated.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIG.
In the second embodiment, the difference from the first embodiment will be mainly described, and the same components as those in the first embodiment will be denoted by the same reference numerals and the description thereof will be omitted.
As shown in FIG. 5A, in this embodiment, the sealing plate slope 151 of the sealing plate 15 is inclined with respect to the back surface 10B, and the support wall slope 141 that follows the sealing plate slope 151 is formed on the support wall 14. Is formed.
The through recess 13 of the present embodiment is formed by a recess slope 18 as a first slope and a support wall slope 141 as a second slope.
The support wall slope 141 and the sealing plate slope 151 are expanded in diameter from the back surface 10B side of the through recess 13 toward the front surface 10A side. The inclination angles of the support wall inclined surface 141 and the sealing plate inclined surface 151 with respect to the back surface 10B do not necessarily coincide with the inclined angle of the recessed portion inclined surface 18 of the through recess 13. Further, the sealing plate slope 151 and the recess slope 18 may not be continuous. In the example of FIG. 5, a surface 17 parallel to the back surface 10 </ b> B is interposed between the support wall slope 141 and the recess slope 18. ing.
On the other hand, the sealing plate slope 151 and the concave slope 18 can be made continuous at the same tilt angle. In this case, in the removal step S <b> 2, the frustoconical range of the composite material 10 is removed, and the peripheral edge portion on the back surface 10 </ b> B side of the through recess 13 formed thereby is used as the support wall 14. If it carries out like this, since the support wall 14 and the penetration recessed part 13 can be formed at once by a scarf process, repair can be made easy.

In the second embodiment, the support wall 14 is formed on the composite material 10 and the support wall slope 141 is formed on the support wall 14 by the same procedure as in the first embodiment. When the sealing plate 15 on which the sealing plate slope 151 is formed is installed on the support wall 14, the sealing plate slope 151 faces the support wall slope 141 as shown in FIG.
After that, as in the first embodiment, the repair material 20 is arranged inside the through recess 13 formed by scarf processing, and after the steps of evacuation, heating, and curing, the repair is performed as shown in FIG. 5B. Is completed.
The composite material 10 so modified can disperse the stress generated in the composite material 10 by the support wall slope 141 and the sealing plate slope 151. This is a case where the sealing plate 15 cannot be made too thin to secure stress, and the height of the bonding surface (the concave slope 18) of the composite material 10 and the repair material 20 to be scarf-joined cannot be sufficiently secured. However, stress concentration can be avoided by the stress distribution formed by the entire support wall slope 141 and the concave slope 18.

In addition to the above, as long as the gist of the present invention is not deviated, the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.
For example, in the above repair procedure, the scarf processing is performed after the sealing plate 15 is installed on the back surface 10B side of the through hole 12, but the sealing is performed after the scarf processing is performed following the formation of the through hole 12. A plate 15 can also be installed. In that case, the sealing plate 15 and the repair material 20 integrated in advance may be disposed in the through recess 13.
Further, the repair material disposed in the through recess 13 is not limited to the repair material 20 described above. The repair material can also be composed of fibers and molten resin. The fiber may be disposed in the through recess 13 and the resin may be impregnated with the resin by pouring molten resin into the through recess 13.
In each of the above-described embodiments, the support wall 14 is formed in an annular shape continuously in the circumferential direction. However, the present invention allows the support wall to have a discontinuous shape in the circumferential direction.
The support wall and the sealing plate in the present invention may be of any specific shape as long as they are used for sealing during evacuation.
Furthermore, the “frustum” in the present invention includes not only the truncated cone disclosed in the above embodiment but also an elliptical truncated cone.
In addition, the composite material in this invention is applicable not only to the outer plate | board of an aircraft wing but to various structures. Especially, since the wing | blade of a windmill is assembled in a box shape similarly to the wing | blade of an aircraft, it is suitable for the outer plate | board of the windmill blade.

DESCRIPTION OF SYMBOLS 10 Composite material 10A Front surface 10B Back surface 11 Damaged part 12 Through hole 13 Through recessed part (through hole)
14 Support Wall 15 Sealing Plate 15A Surface 18 Concave Slope 20 Repair Material 20A Surface 20B Backside 20C Slope 21 Back Film 22 Sealant Tape 23 Vacuum Valve 24 Heater Mat 31 Bottom 32 Top Surface 33 Slope 141 Support Wall Slope 151 Sealing Plate Slope AD Adhesive D Opening diameter D1 Bottom diameter D2 Top surface diameter θ Inclination angle

Claims (12)

In the plate-like composite material formed of fiber and resin, the frustum-shaped range that expands from the back side to the front side is removed, and the composite material is bonded to the repair material in place of the removed portion. A repair method,
A thickness range from the top surface side to the projection area of the top surface on the bottom surface of the frustum from the top surface side, leaving a support wall protruding radially inward from the peripheral edge of the top surface of the frustum A removal step to penetrate through and
A back side sealing step for sealing the back side by installing a sealing plate inserted from the front side into the through hole formed by removal on the support wall;
A repair material placement step of placing the repair material with an adhesive interposed in the composite material from which the frustum-shaped area has been removed, and
Vacuuming step of sealing and vacuuming the surface side,
A method of repairing a composite material characterized by the above. In the removing step, the range from the top surface to the projection region is removed from the frustum-shaped range of the composite material,
After the sealing plate is installed on the support wall, the remainder is removed from the frustum-shaped range.
The method for repairing a composite material according to claim 1. The support wall is formed with a frustum-shaped support wall slope that expands from the back side toward the front side,
Forming a sealing plate slope opposite to the support wall slope on the sealing plate;
The repair method of the composite material of Claim 1 or 2. In the removing step, the frustum-shaped range of the composite material is removed, and the peripheral portion on the back surface side of the frustum-shaped through hole formed by the removal is used as the support wall.
The method for repairing a composite material according to claim 3. The opening diameter (D) of the through hole corresponds to the diameter (D2) of the top surface of the frustum formed by scarf processing.
The repair method of the composite material of any one of Claim 1 to 4. The support wall is formed integrally with the composite material.
The method for repairing a composite material according to any one of claims 1 to 5. The support wall is formed over the entire circumference of the through hole.
The repair method of the composite material of any one of Claim 1 to 6. The support wall is formed in an annular shape having an inner shape and an outer shape,
The method for repairing a composite material according to any one of claims 1 to 7. The sealing plate is composed of at least one CFRP sheet.
The method for repairing a composite material according to any one of claims 1 to 8. The sealing plate slope and the slope of the frustum-shaped range are continued at the same inclination angle,
The method for repairing a composite material according to claim 3. The sealing plate is a perfect circle,
The method for repairing a composite material according to claim 1. The evacuation is performed only from the front side,
The method for repairing a composite material according to any one of claims 1 to 11.

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